Deployed electromagnetic radiation deflector shield assembly

ABSTRACT

Example aspects of an assembly and a method for using a deployed electromagnetic radiation deflector shield are disclosed. The assembly can comprise a deployable deployed electromagnetic radiation deflector shield comprising: a power supply; and an electromagnet configured to generate a magnetic field to deflect radiation; and a spacecraft, wherein the deployed electromagnetic radiation deflector shield is unattached to the spacecraft when deployed from the spacecraft, wherein the deployed electromagnetic radiation deflector shield is deployed at a distance away from the spacecraft, and wherein the distance is configured to prevent the magnetic field generated by the electromagnet from interfering with the spacecraft.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application is a continuation of U.S. application Ser. No.16/740,644, filed Jan. 13, 2020, which is a divisional of U.S.application Ser. No. 15/477,115, filed Apr. 2, 2017, which issued intoU.S. Pat. No. 10,583,939 on Mar. 10, 2020, each of which are herebyspecifically incorporated by reference herein in their entireties.

TECHNICAL FIELD

This invention relates to the protection of manned spacecraft, mannedbase stations as well as sensitive robotic spacecraft from high energysolar (cosmic) radiation, CMEs (Coronal Mass Ejections), or planetary(Jupiter and the like) radiation. It does so without creating a magneticfield or plasma field that impinges on said spacecraft and the like.

BACKGROUND

Spaceflight outside of the Earth's protective magnetic field isdangerous from a cosmic radiation perspective. Inside Earth's magneticfield, where the manned International Space Station (ISS) orbits, theradiation encountered is minimal and almost all is deflected by ourplanet's magnetic fields. However, outside that protective shield, theSun's solar wind (high energy radiation, solar energetic particles orSEPs) consisting of protons, electrons, alpha particles and plasmascontinuously bombards the spacecraft for the months or years ofspaceflight. On occasion the Sun produces a CME (Coronal Mass Ejection)that vastly increases the energy and volume of this radiation. Theseparticles damage human DNA as well as living tissue and can destroysensitive electronics.

The typical remedy has been to harden the electronics and software fromthese high-speed particles and placing heavy shielding in these mannedor sensitive areas. This adds for considerable weight (and cost) to thelaunch vehicle, reducing needed payload, and is passive in nature.

These SEPs and CMEs can be deflected by a magnetic field as known bythose skilled in the art to pass around the spacecraft and not beabsorbed by it. This deflection of solar wind and radiation is wellunderstood to be due to the Lorentz force. However, a magnetic fieldthat is attached to the spacecraft (as seen in prior art) and enclosingit would cause other shielding issues with equipment and would requiremuch more electrical power to operate (due to the need to enclose theentire spacecraft within that attached magnetic field), not to mentionthat it would perturb the data collection and transmissions of thespacecraft. In addition, much like the Van Allen radiation belt aroundthe Earth, the generated magnetic field can capture some of this solarradiation as a plasma within the magnetic torus further impedingscientific data collection with its close position to the spacecraft.

SUMMARY

Disclosed is a deployed electromagnetic radiation deflector shieldcomprising a power supply; and an electromagnet configured to generate amagnetic field to deflect radiation; wherein the deployedelectromagnetic radiation deflector shield is deployed at a distanceaway from one of a spacecraft and a base station to minimize an effectof the magnetic field on the one of the spacecraft and base station.

Also disclosed is a deployed electromagnetic radiation deflector shieldsystem comprising a base station on a planetary surface; a deployedelectromagnetic radiation deflector shield comprising; an electromagnetconfigured to generate a magnetic field to deflect radiation; and aplasma injector configured to inject a plasma gas into the magneticfield to boost the effectiveness of the magnetic field; and a powersupply.

Also disclosed is a method for using a deployed electromagneticradiation deflector shield comprising providing the deployedelectromagnetic radiation deflector shield, the deployed electromagneticradiation deflector shield comprising a power supply and anelectromagnet; deploying the deployed electromagnetic radiationdeflector shield to at least a minimum distance from one of a spacecraftand a base station; and supplying power from the power supply to theelectromagnet to generate a magnetic field to deflect radiation and tocreate a zone of minimum radiation.

A deployed electromagnetic radiation deflector shield assembly isdisclosed, the assembly comprising a base station on a ground surface; adeployed electromagnetic radiation deflector shield comprising anelectromagnet configured to generate a magnetic field configured todeflect radiation from a radiation source; and an upright supporting thedeployed electromagnetic radiation deflector shield at a distance awayfrom the base station, and wherein the distance is configured to preventthe magnetic field from interfering with the base station.

A method for using a deployed electromagnetic radiation deflector shieldis also disclosed, the method comprising providing the deployedelectromagnetic radiation deflector shield, the deployed electromagneticradiation deflector shield comprising a power supply and anelectromagnet; supporting the deployed electromagnetic radiationdeflector shield on an upright, the deployed electromagnetic radiationdeflector shield supported at least a minimum distance from a basestation positioned on a ground surface; and supplying power from thepower supply to the electromagnet to generate a magnetic field todeflect radiation and to create a zone of minimum radiation around thebase station, wherein the minimum distance is configured to prevent themagnetic field from interfering with the base station.

An assembly is disclosed, the assembly comprising a deployable deployedelectromagnetic radiation deflector shield comprising: a power supply;and an electromagnet configured to generate a magnetic field to deflectradiation; and a spacecraft, wherein the deployed electromagneticradiation deflector shield is unattached to the spacecraft when deployedfrom the spacecraft, wherein the deployed electromagnetic radiationdeflector shield is deployed at a distance away from the spacecraft, andwherein the distance is configured to prevent the magnetic fieldgenerated by the electromagnet from interfering with the spacecraft.

Also disclosed is an assembly comprising a deployable first deployedelectromagnetic radiation deflector shield comprising a firstelectromagnet configured to generate a first magnetic field; adeployable second deployed electromagnetic radiation deflector shieldcomprising a second electromagnet configured to generate a secondmagnetic field, wherein the first and second magnetic fields togetherdefine a primary magnetic field; and a spacecraft, wherein the first andsecond deployed electromagnetic radiation deflectors shield are eachdeployed to a distance away from the spacecraft such that the primarymagnetic field does not interfere with the spacecraft.

A method for using a deployed electromagnetic radiation deflector shieldis disclosed, the method comprising deploying the deployedelectromagnetic radiation deflector shield from a spacecraft, whereinthe deployed electromagnetic radiation deflector shield is unattached tothe spacecraft when deployed; moving the deployed electromagneticradiation deflector shield into a desired position relative to thespacecraft; and generating a magnetic field to deflect radiation fromthe spacecraft, wherein the deployed electromagnetic radiation deflectorshield is deployed to a distance such that the magnetic field does notinterfere with the spacecraft.

A deployed magnetic field of a deployed electromagnetic radiationdeflector shield (DERDS) would act like a goalie in a soccer match andmove forward toward the threat (Sun and/or other radiation sources) andreduce the deflection angle needed to have these particles miss aspacecraft. It would provide a magnetopause or zone of minimal radiationin which the spacecraft or an extra-planetary base station would reside.This aspect of the DERDS would be deployed to prevent its own generatedmagnetic field from impinging on the spacecraft and to preventdisturbing data collection or requiring added shielding for it. It wouldalso require a smaller magnetic field and reduce the power requirementsto it. If an electromagnet of the DERDS were cooled sufficiently tobecome superconducting, the strength of the magnetic field would bevastly increased and its electrical power requirements wouldcommensurately lower. It is estimated that a power supply of about 500watts would be all that is required to sustain this electromagneticfield at maximum deflection for most known CMEs. The magnetic fieldstrength can be calculated by Maxwell's equations by those skilled inthe art and incorporated within computer controls of a magnetic fieldgenerator. The DERDS could be maintained at a much lower power settingduring the bulk of a mission, allowing that power to be used for normalspacecraft or an extra-planetary base station requirements. In momentsof intense radiation events (CMEs—alerted by NASA/ESA), allnon-essential power (20 kw+) could be diverted to the DERDS for maximumdeflector shielding. It is envisioned that any long duration mannedspacecraft would have large solar panels as well as RTGs (radioisotopethermal generators), and that manned extra-planetary or moon basestations would also have modular nuclear power units such as molten saltreactors, or liquid fluoride thorium reactors that would produce areliable abundance of electrical power.

The invention (DERDS) provides a magnetic field that will deflect SEPsand CMEs and other harmful solar and cosmic rays away from a mannedspacecraft, robotic spacecraft, or manned extra-planetary base stationsusing an electromagnet that is deployed between the spacecraft/stationand the source of radiation (the Sun and the like) and creates amagnetosphere or zone of minimal radiation in which the spacecraft orbase station would reside.

The invention (DERDS) is deployed to remain between the Sun (orJupiter/Saturn for those missions) and the spacecraft. It utilizes onboard cosmic ray sensors to note the need for the strength of themagnetic field, and on-board sensors to position itself directly in linebetween the Sun/Jupiter/Saturn and the protected spacecraft or station.On board computers and thrusters (it is envisioned as either ion orgaseous) will maintain the required position, so that the magnetic fieldis positioned for the best deflection angle based on incoming SEPs, etc.The deflection by the magnetic field of the incoming particles is wellunderstood, by those skilled in the art, through the Lorentz force. Onlyenough power is generated to provide sufficient deflection. Power isincreased substantially during high threat CMEs.

The DERDS is deployed in space from the protected spacecraft. In oneembodiment, an umbilical cord/tether emanates from the protectedspacecraft to provide electrical power to the DERDS. It also providesback up commands for positioning. The DERDS has on board thrusters toallow it to move into the proper position both in angle and distancefrom the spacecraft. The DERDS can also be mounted on a telescopingsolid mount to the spacecraft and thereby remove the need for thrustersand associated controls to maintain proper magnetosphere positioning, asit would move as a rigid attachment to the spacecraft.

In addition, in an embodiment the DERDS magnetic field can be varied inboth direction, intensity, and time by use of both AC and DC electricalpower inputs and varied as needed to optimize the deflection angle andpower requirements (the field perturbations and strength needed is wellunderstood by those skilled in the arts and utilizes Maxwell's equationsfor calculations). The magnetic field can be perturbed in irregular orset patterns by on board computers and sensors as needed to maintain theproper deflection of these SEPs, CMEs, and other cosmic rays.

On board the DERDS is a super conducting electromagnet that containssufficient cooling (liquid helium, nitrogen etc.) and shielding from theSun to maintain the magnet at superconducting temperatures when neededfor magnetic field strength. It is envisioned that the electromagnet canalso be operated without superconductivity, particularly at the largerdistances from the Sun.

The magnetic field strength of 1×10⁻⁵ Tesla up to 10 Tesla should besufficient to deflect SEPs and other energetic particles of 10 to 50MEV. This should be obtained with nominal 500 watts (or more) ofelectrical power from the protected spacecraft.

In one embodiment, it is envisioned that if the DERDS is not to betethered to the protected spacecraft, and it can be a self-contained butdeployed satellite/spacecraft of its own, having its own foldable solararrays, RTG, or battery power supplies andtransformers/rectifiers/inverters to fluctuate the magnetic field asneeded for optimized performance. It would keep in formation and properposition with its on board sensors and thrusters (much like currentquadcopters drones can maintain formation autonomously).

A reason for this invention to be deployed is to create a magnetic fieldthat will not need to be so large (with a much larger power requirement)as to encompass the entire protected spacecraft, and not allow itsmagnetic field to interfere with said spacecraft. In addition, it isenvisioned that should any charged particles/ions get trapped by theDERDS magnetic field (like Earth's Van Allen Radiation belts), they alsowould not affect the protected spacecraft or extra-planetary basestation. On another embodiment, the DERDS can have a plasma (Barium orLithium) ejector component that can be disbursed into the generatedmagnetic field to increase the field strength (much like a nitro boostin a car engine) when life threatening SEPs or CMEs occur.

The use of the DERDS will reduce the need for additional shielding forlong-range missions from Earth and therefore reduce weight and cost ofthe launch vehicle. It is envisioned that the added weight of the DERDSis lower than the added passive shielding requirements for the sameradiation level protection. Having a DERDS on Jupiter/Saturn missionswould allow greater time for data collection due to the longer timeavailable for orbits than could be had with just wildly eccentric orbitsand passive hardening of the spacecraft. Due to the enhanced protectionby the DERDS from the Jupiter's massive radiation the spacecraft canstay in orbit far longer and collect more data from not only Jupiter,but the Jovian moons of Ganymede, Callisto, Io, and Europa. The samepositive effect would be had on missions to Saturn and its moons.

BRIEF DESCRIPTION OF THE DRAWINGS

The features and components of the following figures are illustrated toemphasize the general principles of the present disclosure.Corresponding features and components throughout the figures may bedesignated by matching reference characters for the sake of consistencyand clarity. Some embodiments of the present invention (DERDS) areillustrated as an example and are not limited by the figures of theaccompanying drawings, in which like references may indicate similarelements and in which:

FIG. 1: FIG. 1 depicts an embodiment of the novel use of the DERDS whereit is shown to be deployed away from the spacecraft and creates a zoneof minimum radiation in which the spacecraft resides. Herein it isdepicted to be tethered to the spacecraft.

FIG. 2: FIG. 2 depicts the deployment of the DERDS via a rigidtelescopic device attached to the spacecraft. This embodiment would notrequire thrusters and associated equipment on the DERDS as it would moveas one when the spacecraft maneuvers. Again, it shows the zone ofminimum radiation created for the spacecraft.

FIG. 3: FIG. 3 depicts a preferred embodiment of the structure andcomponents of the DERDS.

FIG. 4: FIG. 4 depicts an embodiment of a superconducting electromagnetwithin the DERDS.

FIG. 5: FIG. 5 depicts an embodiment of the fully deployed andunattached DERDS. It shows one possibility of where plasma can becontained within a magnetic torus generated by the DERDS. It shows amagnetic field and plasma field positioned away from the spacecraft.

FIG. 6: FIG. 6 is a side view of FIG. 5 illustrating the magnetic fieldand possible plasma field positioned away from the spacecraft.

FIG. 7: FIG. 7 depicts an embodiment of a formation of smaller DERDScreating a larger or differently shaped zone of minimum radiation.

FIG. 8: FIG. 8 illustrates an embodiment of the DERDS as deployed on anecliptic track and providing a large zone of minimum radiation for anextra-planetary or moon base.

FIG. 9: FIG. 9 is a side view of FIG. 8. It shows how the ecliptic trackallows the DERDS to be properly positioned always, as it moves inconcert along the track as the Sun (or other source of radiation) arcsacross the horizon. It thereby keeps the zone of minimum radiationsurrounding the base station as the radiating emitting body moves acrossthe sky.

DETAILED DESCRIPTION

The terminology used herein is for the purpose of describing embodimentsonly and is not intending to be limiting of the invention (also referredto herein as “DERDS”). As used herein, the term “and/or” includes anyand all combinations of one or more of the associated listed items. Asused herein, the singular forms “a,” “an,” and “the” are intended toinclude the plural forms as well as the singular forms, unless thecontext clearly indicates otherwise. It will be further understood thatthe terms “comprises” and/or “comprising,” when used in thisspecification, specify the presence of stated features, steps,operations, elements, and/or components, but do not preclude thepresence or addition of one or more other features, steps, operations,elements, components, and/or groups thereof.

Unless otherwise defined, all terms (including technical and scientificterms) used herein have the same meaning as commonly understood by onehaving ordinary skill in the art to which this invention belongs. Itwill be further understood that such terms, such as those defined incommonly used dictionaries, should be interpreted as having a meaningthat is consistent with their meaning in the context of the relevant artand the present disclosure, and will not be interpreted in an idealizedor overly formal sense unless expressly so defined.

In describing the invention, it will be understood that a number oftechniques and steps are disclosed. Each of these has individual benefitand each can also be used in conjunction with one or more, or in somecases all, of the other disclosed techniques. Accordingly, for the sakeof clarity, this description will refrain from repeating every possiblecombination of the individual steps in an unnecessary fashion.Nevertheless, the specification and claims should be read with theunderstanding that such combinations are entirely within the scope ofthe invention and claims.

In the following description, for the purposes of explanation, numerousspecific details are set forth in order to provide a thoroughunderstanding of the present invention. It will be evident, however, toone skilled in the art that the present invention may be practicedwithout these specific details. The present disclosure is to beconsidered as an exemplification of the invention and is not intended tolimit the invention to the specific embodiments illustrated by thefigures or description below.

FIG. 1: One embodiment of the deployed electromagnetic radiationdeflector shield-4, i.e. the DERDS-4, is deployed by a spacecraft-7using an umbilical/tether device-5. The Sun-1 produces solarradiation-2. The DERDS-4 generates a magnetic field-3 which deflects theincoming radiation-2 and creates a zone of minimum radiation-6 like theEarth's magnetosphere. This is the zone-6 wherein the spacecraft-7 willreside for long durations. It is envisioned that this embodiment of theDERDS-4 will be supplied with electrical power and control of positionby the spacecraft-7 through the umbilical/tether-5. The DERDS-4 canself-maneuver with on board thrusters-26 (shown in FIG. 3) andcomputers-90 (shown in FIG. 3) to keep the DERDS-4 aligned between theSun-1 and the spacecraft-7 throughout the extended range of itsumbilical/tether-5. During the spacecraft's launch, it is envisionedthat the DERDS-4 will be fully retracted and stowed within thespacecraft-7. When the spacecraft-7 needs protection outside of Earth'smagnetic field, the DERDS-4 will be deployed and moved by itsthrusters-26 into the proper distance to establish its magnetic field-3and create the zone of minimum radiation-6. It is envisioned that thisdistance from the spacecraft-7 will ensure minimum interference of thegenerated magnetic field-3 or any plasma-36 (shown in FIG. 5) that getscaught within the magnetic torus, upon the spacecraft-7. It isenvisioned that the spacecraft-7 will orient itself so that the bulk ofit's on board shielding will face the on-coming solar radiation-2 duringCMEs or other high threat radiations.

FIG. 2: One embodiment of the DERDS-4 is deployed by the spacecraft-7using a telescopic device-9. The Sun-1 produces the solar radiation-2.The DERDS-4 generates the magnetic field-3 which deflects the incomingradiation-2 and creates the zone of minimum radiation-6 like the Earth'smagnetosphere. This is the zone-6 wherein the spacecraft-7 will residefor long durations. As the DERDS-4 is solidly attached by the telescopicdevice-9, there is no need for thrusters-26 or their associatedequipment and supplies on the DERDS-4. It is envisioned that thisembodiment of the DERDS-4 will be supplied with electrical power andcontrol of position by the spacecraft-7 through the telescopic device-9.The spacecraft-7 can maneuver to keep the DERDS-4 aligned between theSun-1 and itself. During the spacecraft's launch, it is envisioned thatthe DERDS-4 will be fully retracted and stowed within the spacecraft-7.When the spacecraft-7 needs protection outside of Earth's magneticfield, the DERDS-4 will be deployed and telescoped into the properdistance to establish its magnetic field-3 and create the zone ofminimum radiation-6. It is envisioned that this distance from thespacecraft-7 will ensure minimum interference of the generated magneticfield-3 or any plasma-36 (shown in FIG. 5) that gets caught within themagnetic torus, upon the spacecraft-7. It is envisioned that thespacecraft-7 will orient itself so that the bulk of its on-boardshielding will face the on-coming radiation-2 during CMEs or other highthreat radiations.

FIG. 3—One embodiment of the DERDS-4 is as an independent spacecraftwhich contains a 3-axis thruster control unit-16, a liquid (helium orsimilar) super cooling refrigeration unit-17, a power supply envisionedas an RTG (radioisotope thermal generator)-18, a gas injector-19 (bariumor lithium or the like), alternative embodiment backup power supplyumbilical/tether-5 or telescopic device-9 attached to spacecraft-7,communication unit-21, solar particle sensor unit-22, computerizedstation keeping sensor control unit-23, an electromagnetic generatingunit-24. The DERDS-4 generates a strong magnetic field-3 by using theelectricity from the power supply-18 applied to a super cooledelectromagnet-25 of the electromagnetic generating unit-24. The supercooling refrigeration unit-17 supplies a refrigerant liquid-29 (shown inFIG. 4) in a closed loop system or the like through coils-27 (see FIG.4) surrounding the electromagnet-25 enabling super conductivity of theelectromagnet-25 thereby requiring less electricity for a given neededmagnetic field strength. It is envisioned that an embodiment of thisDERDS-4 can comprise the gas injector-19 configured to inject a plasmagas into the magnetic field-3 to assist the magnetic field-3 indeflecting certain solar radiations-2 or neutralizing certain unwantedcaptured solar plasmas-36 (shown in FIG. 5) in the magnetic torus. TheDERDS-4 will maintain the proper distance from the spacecraft-7 andensure a safe zone of minimum radiation-6 by using its solar particlesensor unit-22 and position itself using its thrusters-26 commanded byits computers-90. Further embodiments of the DERDS-4 have no physicalconnections like the umbilical/tether-5 to the spacecraft-7 oncedeployed. It is envisioned that the DERDS-4 would be release from itsenclosure within the spacecraft-7 when the spacecraft-7 is leaving theprotection of the Earth's magnetic field. Once deployed it will remainin the required formation by use of its thrusters-26 and the computerstation keeping control unit-23. Very little volume of fuel or thrustwould be needed as the DERDS-4 will remain in the required position (dueto Newton's laws) unless the spacecraft-7 alters its trajectory. Whenthat occurs the DERDS-4 will generate similar commands by its own solarparticle sensor unit-22 or back up commands through the communicationsunit-21 and or umbilical/tether-5, to continue to provide that requiredzone of minimum radiation-6 for the spacecraft-7.

FIG. 4: In this embodiment of the electromagnet-25 within the DERDS-4 isthe coil-27 (e.g., copper windings) (or other conducting metal), theinternal power unit for electricity RTG-18 (or fuel cell/spaceshipprovided power or the like), a cooling refrigeration unit-17, and aclosed (or open) loop of the refrigerant liquid-29 (helium, nitrogen orthe like). In this embodiment, it is envisioned that the refrigerantliquid-29 will reduce the temperature of the electromagnetic metal(iron, nickel, chromium and the like) of the electromagnet-25 down tothat temperature in which it will behave as a superconductor (it isenvisioned that this would be close to 25-50° Kelvin). In thisembodiment, the power required to sustain a zone of minimum radiation-6will be much reduced. In addition, when there is a significant SEP/CMEevent or any large blast of radiation-2, the DERDS electromagnet-25 willbe able to produce a much stronger magnetic field-3 and through theLorentz forces keep the radiation-2 well deflected. NASA/ESA (i.e., theNational Aeronautics and Space Administration and the European SpaceAgency) have satellites and Earth bound stations that constantly monitorthe Sun-1 and would be able to communicate with the spacecraft-7 and orDERDS-4 directly to warn of ensuing radiation events. The onboard solarparticle sensor unit-22 (shown in FIG. 3) would also be able to ramp upthe magnetic field-3 when these radiation events arrive.

FIG. 5: With the DERDS-4 in deployed operation, generating a magneticfield-3 which produces the Lorentz forces to deflect the incoming solarradiation-2 from the Sun-1 (or other radiation source like Jupiter orSaturn for those missions). The zone of minimum radiation-6 is therebycreated as the solar radiation-2 has been deflected. It is within thezone-6 where the spacecraft-7 will reside for the duration of itstravel, for example, from Earth to Mars and beyond. This zone-6 willallow sustained operation with minimal additional shield required forthe spacecraft-7. An important embodiment of this DERDS-4 is that themagnetic field-3 generated, and the possible undesirable plasma-36trapped within the magnetic torus (like the radiation trapped within theEarth's Van Allen belts) will not be impinging on the spacecraft-7incurring other undesirable effects on the spacecraft-7.

FIG. 6: This is FIG. 5 rotated to view the DERDS-4 operation from theside. With the DERDS-4 in deployed operation, generating a magneticfield-3 and a deflection limit-39 which produces the Lorentz forces todeflect the incoming solar radiation-2 from the Sun-1 (or otherradiation source like Jupiter or Saturn for those missions). The zone ofminimum radiation-6 is thereby created as the solar radiation-2 has beendeflected. It is within the zone-6 where the spacecraft-7 will residefor the duration of its travel, for example, from Earth to Mars andbeyond. This zone-6 will allow sustained operation with minimaladditional shield required for the spacecraft-7. An important embodimentof this DERDS-4 is that the magnetic field-3 generated, and the possibleundesirable plasma-36 trapped within the magnetic torus (like theradiation trapped within the Earth's Van Allen belts) will not beimpinging on the spacecraft-7 (as seen in prior art) incurring otherundesirable effects on the spacecraft-7.

FIG. 7: In this embodiment, there are there are several DERDS-4 deployedand maintaining formation with one another (much like current quadcopterdrones are able with those skilled in the arts) to maintain a magneticfield-3 that deflects incoming solar radiation-2 from a radiationsource-47 (like the Sun-1, Jupiter or Saturn and the like). Thedeflection due to Lorentz forces creates a zone of minimum radiation-6within which the spacecraft-7 resides for long duration flight. Thiszone-6 can be made larger or have its shape changed by the repositioningof the formation of DERDS-4. When not needed, the additional DERDS-4 canbe re-stowed on board the spacecraft-7, and used as spares for longduration flight. These DERDS-4 can be made smaller in size and havesmaller magnetic field generation capability and use their collectivemagnetic fields-3 for the protection of the spacecraft-7. As thespacecraft-7 goes into less dense solar radiation-2 (in missions toJupiter or Saturn and beyond and the like) the smaller DERDS-4 mightonly be needed singly, with the rest dispatched or re-stowed as spares.It is envisioned in this embodiment that the DERDS-4 so deployed can besmaller and have electromagnets-25 that are not boosted in strength bythe need for super conductivity and the refrigeration needed. In anotherembodiment, the DERDS-4 can be deployed in a formation to deflectradiation-2 from multiple sources such as from the Sun-1 and flight nearJupiter or Saturn. One DERDS-4 protects from the solar radiation-2 andthe other positions itself to deflect the planetary radiation.

FIG. 8: In this embodiment, a manned or unmanned base station-50 on aplanetary body (such as Mars or one of the moons of Jupiter/Saturn andthe like) would need a large zone of minimum radiation-6 and has aDERDS-4 mounted but moveable to be constantly inline between theradiation source-47, such as the Sun-1, and the base station-50. Thisembodiment of the DERDS-4 is deployed on an ecliptic track-54 which issupported by uprights-55 anchored in the surface-56 of a planet or moon.The base station-50 is protected by the zone of minimum radiation-6which is generated by the magnetic field-3 of the DERDS-4. The Sun-1 (orother radiation source-47 like Jupiter or Saturn) creates the incomingsolar radiation-2 and is deflected by the magnetic field-3 through theLorentz forces. It is an embodiment of this DERDS-4 to be deployed sothat its generated magnetic field-3 does not interfere or impinge on thebase station-50. Additionally, any plasmas-36 (shown in FIG. 5) caughtwithin the magnetic fields torus are also kept away from the basestation-50. It is envisioned that any manned base station-50 will needlong-term electrical power and hence in this embodiment the power wouldbe supplied by a modular nuclear reactor of the molten salt variety(liquid fluoride thorium reactor or the like or numerous RTGs-18). Thepower requirements for the base station-50 would likely be from 100kilowatts to 1 megawatt. Additional or back up power could be providedby solar panels-59.

FIG. 9: This is a view of FIG. 8 rotated 90° to better view the DERDS-4on the ecliptic track-54 and the DERDS-4 remaining in line with theradiation source-47 and incoming solar radiation-2 and the basestation-50. In this embodiment, a manned or unmanned base station-50 ona planetary body (such as Mars or one of the moons of Jupiter/Saturn andthe like) would need a large zone of minimum radiation-6 and has aDERDS-4 mounted but moveable to be constantly inline between theradiation source-47 (as it arcs across the horizon) and the basestation-50. This embodiment of the DERDS-4 is deployed on an ecliptictrack-54 which is supported by uprights-55 anchored in the surface-56 ofa planet or moon. The base station-50 is protected by the zone ofminimum radiation-6 which is generated by the magnetic field-3 of theDERDS-4. The Sun-1 (or other radiation source like Jupiter or Saturn andthe like) creates the incoming solar radiation-2 and it is deflected bythe magnetic field-3 through the Lorentz forces. It is an embodiment ofthis DERDS-4 to be deployed so that its generated magnetic field-3 doesnot interfere or impinge on the base station-50. Additionally, anyplasmas-36 (shown in FIG. 5) caught within the magnetic fields torus arealso kept away from the base station-50. It is envisioned that anymanned base station-50 will need long-term electrical power and hence inthis embodiment the power would be supplied by a modular nuclear reactorof the molten salt variety (liquid fluoride thorium reactor or the likeor numerous RTGs-18). The power requirements for the base station-50would likely be from 100 kilowatts to 1 megawatt. Additional or back uppower could be provided by solar panels-59.

That which is claimed is:
 1. An assembly comprising: a deployabledeployed electromagnetic radiation deflector shield comprising: a powersupply; and an electromagnet configured to generate a magnetic field todeflect radiation; and a spacecraft, wherein the deployedelectromagnetic radiation deflector shield is unattached to thespacecraft when deployed from the spacecraft, wherein the deployedelectromagnetic radiation deflector shield is deployed at a distanceaway from the spacecraft, and wherein the distance is configured toprevent the magnetic field generated by the electromagnet frominterfering with the spacecraft.
 2. The assembly of claim 1, wherein thedeployed electromagnetic radiation deflector shield further comprises aplasma injector configured to inject a plasma gas into the magneticfield to boost an effectiveness of the magnetic field.
 3. The assemblyof claim 2, wherein the plasma injector comprises a plasma gas, theplasma gas comprising at least one of barium and lithium.
 4. Theassembly of claim 1, wherein the magnetic field is configured to vary instrength to optimize a zone of minimum radiation.
 5. The assembly ofclaim 1, wherein the deployed electromagnetic radiation deflector shieldfurther comprises a refrigeration unit, the refrigeration unitcomprising a refrigerant configured to reduce a temperature of theelectromagnet.
 6. The assembly of claim 5, wherein the refrigerantcomprises at least one of helium and nitrogen.
 7. The assembly of claim5, wherein the refrigeration unit comprises coils surrounding theelectromagnet, and wherein the refrigerant is transferred through thecoils.
 8. The assembly of claim 1, further comprising a sensorconfigured to sense radiation and a propulsion device configured to movethe position of the deployed electromagnetic radiation deflector shieldrelative to the spacecraft to align the magnetic field with theradiation.
 9. The assembly of claim 8, wherein the propulsion devicecomprises at least one thruster coupled to the deployed electromagneticradiation deflector shield and a thruster control unit configured tocontrol the thruster.
 10. The assembly of claim 1, wherein the deployedelectromagnetic radiation deflector shield is stowed within thespacecraft when not deployed from the spacecraft.
 11. An assemblycomprising: a deployable first deployed electromagnetic radiationdeflector shield comprising a first electromagnet configured to generatea first magnetic field; a deployable second deployed electromagneticradiation deflector shield comprising a second electromagnet configuredto generate a second magnetic field, wherein the first and secondmagnetic fields together define a primary magnetic field; and aspacecraft, wherein the first and second deployed electromagneticradiation deflectors shield are each deployed to a distance away fromthe spacecraft such that the primary magnetic field does not interferewith the spacecraft.
 12. The assembly of claim 11, wherein each of thefirst and second deployed electromagnetic radiation deflector shieldsare unattached to the spacecraft when deployed from the spacecraft. 13.The assembly of claim 11, wherein at least one of the first and seconddeployed electromagnetic radiation deflector shields are stowed withinthe spacecraft when not deployed from the spacecraft.
 14. The assemblyof claim 11, wherein the primary magnetic field creates a zone ofminimum radiation, and wherein the entire spacecraft lies within thezone of minimum radiation.
 15. The assembly of claim 14, wherein thefirst deployed electromagnetic radiation deflector shield isrepositionable relative to the second deployed electromagnetic radiationdeflector shield to adjust at least one of a size and a shape of thezone of minimum radiation.
 16. A method for using a deployedelectromagnetic radiation deflector shield comprising: deploying thedeployed electromagnetic radiation deflector shield from a spacecraft,wherein the deployed electromagnetic radiation deflector shield isunattached to the spacecraft when deployed; moving the deployedelectromagnetic radiation deflector shield into a desired positionrelative to the spacecraft; and generating a magnetic field to deflectradiation from the spacecraft, wherein the deployed electromagneticradiation deflector shield is deployed to a distance such that themagnetic field does not interfere with the spacecraft.
 17. The method ofclaim 16, further comprising sensing radiation with a sensor of thedeployed electromagnetic radiation deflector shield and moving theposition of the deployed electromagnetic radiation deflector shield toalign the magnetic field with the radiation.
 18. The method of claim 16,wherein the deployed electromagnetic radiation deflector shieldcomprises a power supply and an electromagnet, and wherein generating amagnetic field comprises supplying power from the power supply to theelectromagnet.
 19. The method of claim 16, wherein generating a magneticfield creates a zone of minimum radiation, and wherein the entirespacecraft lies within the zone of minimum radiation.
 20. The method ofclaim 19, wherein the deployed electromagnetic radiation deflectorshield is a first deployed electromagnetic radiation deflector shield,the method further comprising: deploying a second deployedelectromagnetic radiation deflector shield from the spacecraft; andrepositioning the first deployed electromagnetic radiation deflectorshield relative to the second deployed electromagnetic radiationdeflector shield to adjust at least one of a size and a shape of thezone of minimum radiation.